Air drag landing anchor device for aircraft



Nov. 28, 1944. 'G, c, ENKNS 2,363,732

' AIR DRAG' LANDING ANCHOR DEVICE FOR AIRCRAFT Filed Aug. 20, 1942 2 Sheets-Sheet l j 3 In 0 en Z01 6. c. Jezwia'zvs J? WWWMZQQ Nov. 28,-1944. e. c. JENKINS 2,353,732

AIR DRAG LANDING ANCHOR DEVICE FOR AIRCRAFT Filed Aug. 20, 1942 2 Sheets-Sheet 2 Patented Nov. 28, 1944 "AIRCRAFT r Gr ali am Claude Jenkins,

Good Hope, Union ofSouthAfric'a Application August 20, 1942, Serial No. 455,486- In the Union of South Africa November 6, 1941 2 Claims. (01. 244-113) This invention relates to an improved air. drag landing anchor device forfaircraft which is adapted to retard the landing speed and so enable an aeroplane on landing to come ,to 'rest' in a shorter distance than heretofore. The ability 7 to do this, besides permitting landing on relatively small aerodromes, is a safety factor when emergency or crash landings have to be made.

According to the invention an air drag land ing anchor device for aircraft'consists of a para-.

chute device adapted to be housed in a chamber adjacent the tail of the machine with means operable from the pilots cockpitor cabinjfor releasing said parachute device from its chamber when required so that it opens out behind the machine and acts as air braking means'to reduce' the flying speed thereof.

More particularly the chamber housing the parachute itself is adapted to open downwardly so that the parachute, on opening of said chamber, falls out by gravitational action clear of any part of the tail of the machine. The parachute is anchored to a suitable point adjacent the tail of the machine by means of a cable, with an interposed swivel connection to prevent twisting of the suspension cords thereof.

The opening of the chamber is adapted to be effected by a simple operation such as the movement of a conveniently placed hand lever along side the pilots seat. A draw-in rope or cable passingover winding means and attached adja- Fig 4 is a part-sectional elevation of the swivel connectionfor the parachute,

Fig. 5 is a fragmentary plan view of the front. end of the swivel connection shown in Fig. 4, and

, Fig. 6 is a perspective view showing the relationship of the parachute to an aeroplane, when in the fully open position.

Referring to the drawings, reference I denotes the rear portion of an aeroplane having a chamber 2, for housing a parachute 3, located towards the tail end of the machine. in the form of a cylindrical container having an opening in its bottom side adapted to be closed byan arcuate door 4 mounted for partial rotary movement on pintles 5 journalled in the end walls of the casing of the container 2. The said door 4 is arrangedto be opened by means of a lever arm 6 keyed to one of the 'pintle pins 5 and connected by a link rod 1 to an operating hand lever 8 located in the cockpit 9.

The parachute 3 which is substantially of conventional design, is connected through a swivel connection I 0 to an anchoring cable ll passing through an anchor shackle l2, securely fixed to the fuselage. 'A draw-in cable I3 attached adjacent the centre air release opening [4, has its cent the centre air release opening in the parachute, is provided for hauling in the parachute after use. It will be understood that the action of drawing in the parachute centre first, allows for rapid spilling of the airtherefrom as soon as the plane has landed, and thereby prevents the machine from being blown backwards in the event of a landing being made in a strong wind.

To enable the invention to be more clearly understood and carried into practice, reference is now made to the accompanying drawings, in which like references denote like parts throughout the several views.

In the drawings:

Fig. 1 is a shortened part-cut-away side elevation of the rear portion of an aeroplane fitted with apparatus constructed according to themvention and showing the parachute in its housed position.

Fig. 2 is a similar view to that of Fig. 1, but

showing the parachute a moment after its re-,

lease,

Fig. 3 is aplan view taken on'Fig. 2.

' opposite end secured to a small reeling drum l5,

likewise located in the cockpit 9. This cable l3 passes through a central bore in the swivel connection. Ill. The winding drum I5 is provided witha ratchet stop lever I6 co-acting with a ratchet wheel H, to facilitate the reeling in operation.

Figs. 4 and 5 illustrate in more detail'the swivel connection In which consists of an inner I or front part I1, rotatably mounted by the ball races 19 within an outer or rear part I8 having a holed flared skirt portion 20 to which the parachute cords are attached. The'inner part I! is provided with acentral bore. 22' through which the draw-in cable l3 passes, while its front end isbifurcated andthe two arms 2| provided with holes 23 for the attachment thereto of the anchoring cable H n In operation the several parts of the apparatus will normally be in thevpositions shown by Fig. '1. When the pilot desires to release the paraa chute 3, he moves the stop lever l6 and the hand lever 8 to the positions' shown in Fig. 2. These motions allow the folded parachute 3 to drop out below the tail of the machine, by opening the door 4 and allowing the draw-in cable I3 to be freely reeled off the drum I5. Immediately after release the parachute opens and trails out be The chamber 2 is hind the machine to act as an air brake, as clearly shown in Fig. 6.

When, after landing, it is desired to re-house the parachute, the winding drum I5 is rotated to haul in the cable I3. This has the effect of turning the parachute inside out so as to spill the air therefrom and enable it to be folded and replaced in the container 2' ready for re-use.

If considered advisable, more than one para-' chute device may be fitted to a machine.

What I claim is:

1. A motion retarding device for aircraft cornprising a cylindrical container located adjacent the tail of the aircraft and having. an opening, in the underside thereof, an arcuate door for closing said opening and mounted for rotation about the axis of the cylindrical container, a parachute attached to the aircraft and normally enclosed in said container and supported by said door whereby when said door is opened the parachute may descend by gravity, an operating lever pivotally mounted in the aircraft and connectd with said door.

2. A motion retarding device as claimed in claim 1, characterized by the provision of a drawin cable connected with said parachute, and a winding drum for said cable rotatably mounted coaxially of said lever.

GRAHAM CLAUDE JENKINS. 

